US10415422B2 - Method for operating a turbo-machine having overload protection and turbo-machine comprising a device for carrying out said method - Google Patents

Method for operating a turbo-machine having overload protection and turbo-machine comprising a device for carrying out said method Download PDF

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Publication number
US10415422B2
US10415422B2 US15/024,457 US201415024457A US10415422B2 US 10415422 B2 US10415422 B2 US 10415422B2 US 201415024457 A US201415024457 A US 201415024457A US 10415422 B2 US10415422 B2 US 10415422B2
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United States
Prior art keywords
rotary shaft
turbomachine
torque
stage
overload protection
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Expired - Fee Related, expires
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US15/024,457
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English (en)
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US20160230591A1 (en
Inventor
Hans-Gerd Brummel
Dirk Grieshaber
Carl Udo Maier
Uwe Pfeifer
Huub De Bruyn
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Siemens Energy BV
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Siemens AG
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Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Grieshaber, Dirk, BRUMMEL, HANS-GERD, PFEIFER, UWE, MAIER, CARL UDO
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIEMENS NEDERLAND N. V.
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Assigned to SIEMENS ENERGY B.V. reassignment SIEMENS ENERGY B.V. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIEMENS AKTIENGESELLSCHAFT
Expired - Fee Related legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/14—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L3/00—Measuring torque, work, mechanical power, or mechanical efficiency, in general
    • G01L3/02—Rotary-transmission dynamometers
    • G01L3/04—Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft
    • G01L3/10—Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft involving electric or magnetic means for indicating
    • G01L3/101—Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft involving electric or magnetic means for indicating involving magnetic or electromagnetic means
    • G01L3/102—Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft involving electric or magnetic means for indicating involving magnetic or electromagnetic means involving magnetostrictive means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the following relates to a method for operating a turbomachine having overload protection.
  • the turbomachine has at least one turbomachine stage.
  • a turbomachine having a device for carrying out the method is specified.
  • a turbomachine energy is transferred by a flowing fluid (gas or liquid).
  • the energy transfer takes place in this case via a rotor with a rotary shaft (driveshaft or output shaft).
  • a rotary shaft driveshaft or output shaft.
  • rotor blades, wings or blades Arranged on the rotary shaft are rotor blades, wings or blades which are formed such that a pressure difference ( ⁇ p) arises in the fluid flow (volumetric flow rate) between the front side and the rear side of the rotor.
  • An aspect relates to a turbomachine having at least one turbomachine stage which has at least one rotary shaft, wherein the method provides overload protection for the rotary shaft, and, for the overload protection of the rotary shaft, a torsional stress in the rotary shaft during operation of the rotary shaft is sensed.
  • turbomachine having at least one turbomachine stage which has at least one rotary shaft, wherein the turbomachine has a device for carrying out the method.
  • the turbomachine is for example a turbocompressor which has a plurality of compressor stages (turbomachine stages).
  • the method can be used for a single-stage turbomachine.
  • the turbomachine has only one turbomachine stage.
  • a multistage turbomachine having at least one further turbomachine stage is used as the turbomachine, said further turbomachine stage having at least one further rotary shaft.
  • the method provides overload protection for the further rotary shaft, and, for the overload protection of the further rotary shaft, a further torsional stress in the further rotary shaft during operation of the further rotary shaft is sensed.
  • the turbomachine has at least one further turbomachine stage having at least one further rotary shaft.
  • the rotary shaft and the further rotary shaft are identical.
  • such a multistage turbomachine is a multistage turbocompressor.
  • the basic idea of embodiments of the invention is that of determining the torsional torque at the rotary shaft and/or the further torsional torque at the further rotary shaft during operation of the turbomachine.
  • the torsional torques determined are used for the overload protection of each particular rotary shaft.
  • each of the rotary shafts is preferably treated separately.
  • the methods for sensing the torsional stress and for sensing the further torsional stress are carried out independently of one another.
  • a torque of the rotary shaft is measured and/or, in order to sense the torsional stress in the further rotary shaft, a further torque of the further rotary shaft is measured.
  • the particular torque is in this case preferably measured continuously.
  • a temporal change in the torque can be sensed.
  • the development of the torque is estimated.
  • a prediction (forecast) for the development of the torque is established.
  • the development of the torque is forecast or extrapolated. Whether the permissible limit value M lim for the torque is exceeded is estimated using the forecast. In this case, countermeasures are taken.
  • At least one operating parameter of the turbomachine stage is changed such that the limit value M lim for the rotary shaft is not exceeded but is complied with.
  • the volumetric flow rate of the fluid with which the turbomachine or the turbomachine stage is operated is changed.
  • the operating parameter of the turbomachine stage is the volumetric flow rate. It is also conceivable, on the basis of the forecast, to change a rotational speed at which the rotary shaft of the turbomachine stage is operated. Thus, the turbomachine, or the turbomachine stage, could be shut down or deactivated (rotational speed 0).
  • the operating parameter is the rotational speed of the rotary shaft of the turbomachine stage.
  • Other operating parameters are for example a setting of the orientation of baffles for the flowing fluid.
  • a torque sensor for measuring the torque of the rotary shaft is arranged at the rotary shaft and/or a further torque sensor for measuring the further torque of the further rotary shaft is arranged at the further rotary shaft.
  • the torque and further torque and optionally the temporal changes thereof can be measured independently of one another.
  • At least one of the torque sensors is preferably arranged directly at the particular rotary shaft. With the aid of the torque sensor, the torque at the rotary shaft is measured directly.
  • a compressor has a plurality of compressor stages where each case has one compressor housing. For each of the compressor housings, the torque is measured separately as a torque difference between the driveshaft and output shaft.
  • a contactless measurement method is carried out.
  • the torque sensor and/or the further torque sensor are a contactless torque sensor.
  • An optical measurement method for example is carried out as the contactless measurement method.
  • the contactless measurement method is carried out with the aid of a magnetoelastic torque sensor.
  • the contactless torque sensor is a magnetoelastic torque sensor.
  • Magnetoelasticity is based on a change in the magnetic permeability of a ferroelectric material on account of mechanical forces which act on the ferromagnetic material. As a result of the use of magnetoelastic torque sensors, it is possible to measure torques directly during operation of the turbomachine.
  • a rotary shaft of the turbomachine stage which consists entirely of ferroelectric material.
  • the rotary shaft it is also conceivable for the rotary shaft to consist only in part of ferroelectric material.
  • a ferroelectric coating of the rotary shaft which is connected firmly to the rotary shaft, consists of ferroelectric material. This ensures that, as a result of the connection of the ferroelectric coating and the rotary shaft, the torque of the rotary shaft can be transmitted to the ferroelectric coating.
  • the permeability of the ferroelectric material of the ferroelectric coating changes. This results in a detectable signal which allows conclusions to be drawn about the torque at the rotary shaft.
  • turbomachine is selected from the group consisting of gas turbine, steam turbine, turbocharger, pump, compressor and hydro turbine.
  • the turbomachine is a compressor, in particular a turbocompressor.
  • a turbocompressor is understood to be both mechanically driven compressors in the oil and gas sector and combined machines for energy conversion such as gas turbines.
  • overloads can be extrapolated and forecast early. This applies in particular in the case of sufficiently small temporal changes.
  • Such a dynamic process is used to prevent the overload limit from being exceeded or overshot.
  • FIG. 1 shows a single-stage single-shaft compressor
  • FIG. 2 shows a multistage single-shaft compressor
  • FIG. 3 shows a geared compressor
  • FIG. 4 shows a forecast development of a torque using measured torques.
  • turbomachine 1 in the form of a turbocompressor having at least one compressor stage (turbomachine stage) 11 .
  • the compressor stage 11 has a rotary shaft 111 .
  • the torque sensor 112 is a magnetoelastic torque sensor.
  • the turbocompressor 1 has a device 100 for carrying out a method for operating the turbocompressor 1 , wherein
  • the rotary shaft 111 consists of ferroelectric material.
  • the rotary shaft 111 has a ferroelectric coating that is connected firmly to the rotary shaft 111 .
  • At least one operating parameter of the compressor stage 11 is varied.
  • the operating parameter is the rotational speed 115 of the rotary shaft 111 , which is changeable via the actuation of the motor 13 , and/or the volumetric flow rate of the fluid, which is changeable via the volumetric flow rate orifice plate 114 .
  • the turbocompressor 1 is an (axially or radially operated) single-shaft compressor (compressor with only one rotary shaft) having only one compressor stage ( FIG. 1 ).
  • the front side of the compressor stage is indicated by the reference sign 116 and the rear side of the compressor stage by 117 .
  • turbocompressor 1 is a multistage single-shaft compressor ( FIG. 2 ).
  • the turbocompressor 1 has a turbocompressor stage 11 and at least one further turbocompressor stage 12 .
  • the rotary shaft 111 of the compressor stage 11 and the further rotary shaft 121 of the further compressor stage 12 form a common rotary shaft.
  • a further magnetoelastic torque sensor 122 Arranged at the further compressor stage 12 is a further magnetoelastic torque sensor 122 . With the aid of the further torque sensor 122 , the further torque is tapped in the region of the further rotary shaft 121 .
  • the torque sensor 112 and the further torque sensor 122 are operated independently of one another.
  • the turbocompressor 1 is a geared compressor ( FIG. 3 ).
  • the compressor stage 11 and the further compressor stage 12 are connected together via a gear mechanism 14 .
  • the rotary shaft 111 is driven via the motor 13 .
  • the further rotary shaft 121 is coupled to the rotary shaft 111 via the gear mechanism 14 .
  • the torque of the rotary shaft 111 is measured via the torque sensor 112 and the further torque of the further rotary shaft 121 is measured via the further rotary torque sensor 122 .
  • the fluid to be compressed is introduced into the geared compressor and the compressed fluid is removed from the geared compressor again by the adjustable input control apparatus (ELA) 310 and the adjustable output control apparatus (ALA) 320 , respectively.
  • volumetric flow rate orifice plate 330 Further constituent parts are a volumetric flow rate orifice plate 330 and devices for measuring the pressure differences 340 and 350 at the individual compressor stages 11 and 12 .
  • FIG. 4 indicates how, on the basis of the measured torques 40 , the ongoing development of the torque 41 can be forecast.
  • a particular torque limit value M lim ( 42 ) is reached.
  • This limit value can be an alarm value and act as a boundary signal.
  • operating parameters of the turbocompressor 1 or the compressor stages thereof, would be changed such that the alarm value is not reached.
  • the alarm value 41 acts as a switch-off signal: the forecast reaching of the alarm value results in the turbocompressor 1 being switched off.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • General Physics & Mathematics (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
US15/024,457 2013-09-30 2014-09-05 Method for operating a turbo-machine having overload protection and turbo-machine comprising a device for carrying out said method Expired - Fee Related US10415422B2 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE102013219752 2013-09-30
DE102013219752.7 2013-09-30
DE102013219752 2013-09-30
PCT/EP2014/068893 WO2015043914A1 (fr) 2013-09-30 2014-09-05 Procédé d'exploitation d'une turbomachine avec protection contre les surcharges et turbomachine équipée d'un dispositif permettant la mise en œuvre de ce procédé

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US20160230591A1 US20160230591A1 (en) 2016-08-11
US10415422B2 true US10415422B2 (en) 2019-09-17

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US (1) US10415422B2 (fr)
EP (1) EP3036408B1 (fr)
CN (1) CN105765172B (fr)
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Cited By (1)

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US11168621B2 (en) * 2019-03-05 2021-11-09 Pratt & Whitney Canada Corp. Method and system for operating an engine in a multi-engine aircraft

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Publication number Priority date Publication date Assignee Title
US10871409B2 (en) 2017-12-15 2020-12-22 G.E. Avio S.r.l. SMD-coil-based torque-sensor for tangential field measurement
US11493407B2 (en) 2018-09-28 2022-11-08 Ge Avio S.R.L. Torque measurement system
CN110726502B (zh) * 2019-10-21 2025-08-01 无锡锡压压缩机有限公司 一种调节螺杆压缩机阴转子力矩的方法
US11674412B2 (en) * 2021-04-16 2023-06-13 Baker Hughes Holdings Llc Closed loop control employing magnetostrictive sensing

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US11168621B2 (en) * 2019-03-05 2021-11-09 Pratt & Whitney Canada Corp. Method and system for operating an engine in a multi-engine aircraft

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EP3036408A1 (fr) 2016-06-29
CN105765172B (zh) 2018-03-27
US20160230591A1 (en) 2016-08-11
CN105765172A (zh) 2016-07-13
EP3036408B1 (fr) 2019-11-27
WO2015043914A1 (fr) 2015-04-02

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